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Accession Number N20120012531
Title Mission Life Thermal Analysis and Environment Correlation for the Lunar Reconnaissance Orbiter.
Publication Date Jul 2012
Media Count 9p
Personal Author H. Peabody M. B. Garrison
Abstract Standard thermal analysis practices include stacking worst-case conditions including environmental heat loads, thermo-optical properties and orbital beta angles. This results in the design being driven by a few bounding thermal cases, although those cases may only represent a very small portion of the actual mission life. The NASA Goddard Space Flight Center Thermal Branch developed a procedure to predict the flight temperatures over the entire mission life, assuming a known beta angle progression, variation in the thermal environment, and a degradation rate in the coatings. This was applied to the Global Precipitation Measurement core spacecraft. In order to assess the validity of this process, this work applies the similar process to the Lunar Reconnaissance Orbiter. A flight-correlated thermal model was exercised to give predictions of the thermal performance over the mission life. These results were then compared against flight data from the first two years of the spacecraft's use. This is used to validate the process and to suggest possible improvements for future analyses.
Keywords Correlation
Lunar orbiter
Optical properties
Temperature effects
Thermal analysis
Thermal environments

Source Agency National Aeronautics and Space Administration
NTIS Subject Category 46B - Fluid Mechanics
84 - Space Technology
Corporate Author Goddard Space Flight Center, Greenbelt, MD.
Document Type Conference proceedings
Title Note N/A
NTIS Issue Number 1303
Contract Number N/A

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